Formulas and charts for the supersonic lift and drag of flat swept-back wings with interacting leading and trailing edges

Abstract : The problem is considered of a wing with rectilinear plan form swept so that both leading and trailing edges lie within their respective Mach cones; moreover, the Mach lines from the trailing edge apex intersect the leading edge. Formulas and design charts are presented for the lift in such a case, based on approximate formulas for the lift distribution developed in NACA TN 1991, l949.